EP3470769A1 - Projectile d'armes de petite taille - Google Patents

Projectile d'armes de petite taille Download PDF

Info

Publication number
EP3470769A1
EP3470769A1 EP17196685.6A EP17196685A EP3470769A1 EP 3470769 A1 EP3470769 A1 EP 3470769A1 EP 17196685 A EP17196685 A EP 17196685A EP 3470769 A1 EP3470769 A1 EP 3470769A1
Authority
EP
European Patent Office
Prior art keywords
projectile
diameter
equals
base
dimples
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP17196685.6A
Other languages
German (de)
English (en)
Inventor
Dennis Omanoff
John D. Taylor
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Next Generation Tactical LLC
Original Assignee
Next Generation Tactical LLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Next Generation Tactical LLC filed Critical Next Generation Tactical LLC
Priority to EP17196685.6A priority Critical patent/EP3470769A1/fr
Priority to MX2017014723A priority patent/MX2017014723A/es
Priority to US15/919,307 priority patent/US20190113318A1/en
Publication of EP3470769A1 publication Critical patent/EP3470769A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins
    • F42B10/08—Flechette-type projectiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/44—Boat-tails specially adapted for drag reduction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/02—Driving bands; Rotating bands

Definitions

  • the present disclosure relates to a small arms projectile.
  • MV muzzle velocities
  • 3000 fps 915 m/s
  • To increase the MV one needs to increase the powder charge with a larger cartridge case and/or reduce the projectile weight.
  • Higher velocities can lead to projectile point of impact at greater distances while lower projectile weight can be subject to adverse environmental factors such as lateral drift from crosswinds.
  • Muzzle velocities (MV) are not measured at the muzzle but instead, are measured 10 to 15 feet ( ⁇ 3 to 4,5 m) away from the muzzle with an instrument called a Chronograph. So the velocity of the projectile is measured in flight a short distance from the muzzle just as the gyroscopic spin begins to stabilize the projectile.
  • the boat-tail design projectile made its appearance in the late 19th century.
  • the designs, particularly at a 7.5 degrees configuration decrease base drag thus enhancing greater flight distances before impact.
  • VLD Very Low Drag
  • MV muzzle velocities
  • the common thread running through these exceptions were MV greater than 2800 fps with calibers in the low 20's with low weights.
  • Experimental examples of low weight .30 caliber projectiles are found with MV up to 3500 fps - a .30-06 caliber.
  • a Power Point Transmission (PPT) of a proposed .65 caliber tubular 556gr projectile with estimated MV of 5000 fps is also reported.
  • PPT Power Point Transmission
  • drag is defined as a partial restriction of forward motion of a projectile through air.
  • Shock waves at the projectile's nose and tail - anterior to the boat tail if the projectile has a boat tail - as well as elongated turbulent eddies of air at the base of the projectile are the components of total drag. The latter will lead to the lowering of pressure, and in some cases, leads to a partial vacuum with the loss of kinetic energy of the projectile.
  • BS Bow Shock
  • OS Oblique Shock
  • the laminar boundary layer exhibits a very smooth flow of air molecules, while the turbulent boundary layer contains swirls or "eddies" of air molecules.
  • the laminar flow creates less surface friction drag than the turbulent flow, but is less stable.
  • the smooth laminar flow breaks down and transitions to a turbulent flow.
  • the physics here is based on wing drag and not rotating projectile drag - however one study with rotating projectiles show that both plane and rotating body are similar except the latter are compressed. With regard to rotating bodies, the Magnus Force (MF) must be considered. A number of variables are involved in the MF, but the bottom line is a twist to the projectile in flight. This causes a distortion in the boundary layer leading to an asymmetric profile thickness.
  • base drag contributes approximately 30 to 50% total drag of a rotating projectile through air.
  • a boat tail configuration at the base of the projectile focuses eddies of air and reduces the drag.
  • a 7° boat-tail configuration is considered to give the best performance.
  • Base Bleed has been shown to reduce projectile's base drag.
  • Base Bleed has not been shown to be successful in small arms projectiles.
  • Rotating projectiles such as bullets are more difficult to control than non-rotating projectiles such as rockets. Even though both exhibit similar ballistic characteristics in flight, there are distinct differences - maneuverability being the most notable example.
  • the emergence of the extra-long distance projectile came into being with the .408 Cheyenne Tactical1.
  • the .408 projectile was based on the concept of Balance Flight (see e.g. US 6,629,669 B2 ). It is also known from US 8,573,129 B1 to use a single sealing ring to improve the propulsion effect (interior ballistics).
  • the problem also pertains for so-called non-sabot armor-piercing projectile designs.
  • Modern small arms armor-piercing projectiles are made of two components: A jacket of a metal (e.g. copper) alloy soft enough to be engraved by the barrel's rifling and an inner core made up to a highly dense material (e.g. tungsten carbide, depleted uranium, hardened tool steel).
  • a number of studies show that depleted uranium shows potential health risks to those handling the cartridges and as a result, more than likely will be phased out with time.
  • NanoSteelTM and Liquidmetal® are two such examples.
  • One popular approach is to improve use of tungsten carbide designs without going to increased weights and at the same time to obtain the same ballistic properties as shown above.
  • a projectile having an elongated body extending in a longitudinal direction comprising
  • the present invention is focussed on a type of superior very long-range projectiles to determine a "common thread of characteristics" in order to create a "perfect design” no matter the caliber.
  • Such a projectile comprises a nose portion, a base portion and a middle portion connecting the nose portion and the base portion. Flight and/or propulsion characteristics are improved by structural surface arrangements, which form an aerodynamical effective surface and/or a sealing arrangement comprising a plurality of ductile annular sealing areas.
  • Such an aerodynamical effective surface improves the exterior ballistic properties wherein a sealing arrangement comprising a plurality of ductile annular sealing areas improves the interior ballistic characteristics by forming an effective sealing area between the projectile and the grooves and the lands during propulsion.
  • the deformed ductile annular sealing areas which carry the interior profile of the barrel may also form an aerodynamical effective surface which affects the flight dynamic properties of the projectile surfaces.
  • One embodiment shows a projectile, wherein the projectile has a solid body of revolutionary shape, the nose portion has an ogive shape having a first length L1 the middle portion has a cylindrical shape defining the bearing surface with a diameter D1 and a second length L2, and the base portion has a frustro conical shape having a third length L3.
  • the first length L1 equals 3 to 3.5 times, preferably 3.1 to 3.25 times of the diameter D1
  • the second length L2 equals 1 to 2 times, preferably 1.25 to 1.5 times of the diameter D1
  • the third length L3 equals 0.1 to 1.5 times, preferably 0.1 to 1.1 times of the diameter D1.
  • Embodiments which are within the above range are given according to the following table, wherein D1 characterizes the bullet diameter or calibre, L characterizes the overall length, L2 characterizes the length of the middle portion (or bearing surface range), L1 identifies the length of the nose portion (ogive length) and L3 identifies the length of the base portion (boat tail length).
  • D1 characterizes the bullet diameter or calibre
  • L characterizes the overall length
  • L2 characterizes the length of the middle portion (or bearing surface range)
  • L1 identifies the length of the nose portion (ogive length)
  • L3 identifies the length of the base portion (boat tail length).
  • the values in brackets are in the metric system and show the values in millimetres (mm), wherein the values without brackets are given in inches.
  • ogive shape specifically one of the following shapes: tangent ogive, secant ogive, blunted ogive, spherical blunted ogive, Haack series, von Kármán.
  • Different shape characteristics can be selected for different applications.
  • VLD designs which are suitable for projectiles which maintain for a very long distance in a supersonic state the ogive shape may have a very strong influence on the exterior ballistics (arrange, stability).
  • the structural surface arrangement comprises at least one of: dimples, nubs, ribs, flutes and grooves.
  • Such structural surface arrangement either formed into the projectile surface (or parts/sections thereof) or obtained during propulsion within the barrel by engraving the interior barrel surface into the exterior projectile surface, may affect the aerodynamic properties, specifically in the boundary layer flow in close proximity to the projectile surface.
  • the structural surface arrangement comprises dimples which have a spherical segment shape with a base diameter DB and a depth d wherein the base diameter DB equals .05 to .3 times the diameter D1 (caliber) of the projectile and the depth d equals .015 to .13 times the diameter D1.
  • the base diameter DB equals .05 to .3 times the diameter D1 (caliber) of the projectile and the depth d equals .015 to .13 times the diameter D1.
  • the dimples are arranged in different sections, namely only in the nose portion or only in the base portion or in both, the nose portion and the base portion. In these areas, the dimple structure is not affected by the interior barrel structure during propulsion.
  • the dimples are arranged in a way that the minimum center-to-center distance DC between adjacent dimples equals the base diameter DB.
  • Such a design allows for a dense arrangement of the dimples at the surface.
  • the dimples can have a center-to-center distance ranging from one to two times the base diameter DB, depending on the dimple size and pattern.
  • the dimples are arranged in a pattern of parallel rows and circles, staggered rows and circles or randomly or a combination of these patterns.
  • the dimples can be arranged so that the outer edges can be either touching or not touching.
  • Such patterns may allow for specific ballistical effects, especially for rotating projectiles.
  • longitudinal flutes are arranged equally interspaced in a circumferential direction in the nose and/or the middle portion.
  • These flutes or grooves serve as vortex generators (of varying numbers, widths and depths) at a distance behind a projectile tip to "bleed off” a percentage of the bow shock wave.
  • the so called “bow shock wave” is formed at the tip of a rotating projectile in a specific distance in the flight direction.
  • a vortex effect achieved by the flutes in the ogive section reduces the distance between the bow shock front and the tip of the projectile and thereby reduces the drag coefficient and increases the velocity of the projectile.
  • the aerodynamical effects of such flute arrangements are therefore suitable to bleed off the bow shock waves.
  • each flute is tapered at each end and has a triangular cross section and a maximum depths DG of 0.025 to 0.4 times the diameter D1 and has a curved bottom line wherein the radius RB of the bottom line equals .25 to 25 x the diameter D1.
  • This design range allows for an adaption of the vortex/flute design to specific requirements.
  • a plurality of fins extend from the base portion (boat tail portion) in a radial direction being inclined by an angle ⁇ of 10° to 30° in relation to a longitudinal axis and have a curved shape of a radius R.
  • Boat-tail (aka boattail) projectiles displays a smaller base diameter than a flat base projectile and thus reduces the volume of vacuum behind the projectile leading to greater stability. Boat-tail or end sections tapered at ⁇ 7.5 degrees are considered standard.
  • Base drag has been estimated to be as high as 30 to 50% of total drag.
  • the drag is related the volume of the vacuum behind the base. Boat tails reduce this volume. It has been demonstrated that embodiments with four or eight blades (fins), perpendicular to the surface of the boat tail and not in a position to be engraved by the lands and grooves reduce the vacuum behind the projectile base.
  • the outer diameter of the fins, diameter D2 is less than the bearing surface diameter D1 so that the fins do not make contact with the barrel lands and grooves.
  • the fins can either be right or left handed depending on the barrel's twist rate.
  • a right handed barrel and a right handed fin should result in extended distance of flight as well as extended velocity.
  • a right handed barrel and a left handed fin would result in reduced distance and velocity. This might be advantageous in certain tactics.
  • the ideal angle of fin curvature has to be determined as clearly the angle would influence the amount of vacuum behind the projectile.
  • Embodiments according to the above fin concept comprise four or eight blades perpendicular from the surface of the boat tail as a novel design to increase or reduce velocity and/or distance of projectile flight.
  • the sealing arrangement comprises a first ductile annular sealing area comprising a front sealing ring and a second annular sealing area comprising a rear sealing ring, wherein the sealing rings are arranged in the middle portion.
  • each sealing ring is arranged between adjacent annular grooves, which have a diameter less that the diameter D1. This allows for a low friction deformation of the sealing ring because the ring volume, which is pushed aside by the barrel rifling during traveling in the barrel, can be received by these annular grooves without affecting or displacing the outside surface of the middle area.
  • a profile shape may be rectangular, semi-circular, cone shaped, trapezoid, parabolic, hyperbolic or similar.
  • first sealing ring has a first diameter DS 1 and the second sealing ring has a second diameter DS 2 , wherein the first diameter DS 1 is larger/lower than the second diameter DS 2 .
  • An additional (first or second) sealing ring with a lower diameter may increase the sealing effectiveness of the first sealing ring which will be partially destroyed by the lands and the grooves of the barrel without increasing the internal friction during propulsion through the barrel.
  • a copper jacketed projectile surrounds a penetrator. It leads to an armor-piercing projectile with a penetrator inside the projectile.
  • Such a solid design gives the projectile some armor-piercing capabilities over what would be found in a lead-core copper jacketed non-armor piercing projectile.
  • an armor-piercing projectile can be designed so that the linear drag on the projectile is matched to its rotational drag, so that the forward rate of deceleration and an axial rate of deceleration are balanced.
  • the penetrator contains one of the following: tungsten carbide, borron carbide, hardened tool steel, oil hardened drill rod and so called nano steel material.
  • the projectile has an elongated body extending in a longitudinal direction along a longitudinal axis 2 and comprises three sections, namely a nose portion 3 (ogive sections), a base portion 4 (boat tail section) and a middle portion 5 connecting the nose portion 3 and the base portion 4.
  • the nose portion 3 has an ogive shape, which starts at the front end of the cylindrical middle portion 5 and ends in a blunted tip 6.
  • the base portion 4 extends from the rear end of the middle portion 5 and has a frustro conical shape with an inclination angle ⁇ of about 7.5°.
  • the cylindrical middle portion 5 has a cylindrical shape of a diameter of D 1 , which is typically in a range of .17 to .80 inches (4.3 to 20 mm) for a small arms projectile.
  • the nose portion 3, the base portion 4 and/or the middle portion 5 comprise a structural surface arrangement, which forms an aerodynamical effective surface, which is not explicitly shown in Fig. 1 but only indicated by little circles 7, which indicate a surface structure comprising dimples, nubs, ribs, flutes and grooves or other.
  • Fig. 2 shows a second embodiment of the present invention in which the middle portion 5 shows a structural surface arrangement, which forms a sealing arrangement comprising a plurality of ductile annular sealing areas 8 and 9.
  • Both the first sealing area 8 and the second sealing area 9 comprise a sealing ring, namely a front sealing ring 10 and a rear sealing ring 11.
  • the front sealing ring 10 and the rear sealing ring 11 have an outer diameter DS, which is larger than the diameter D1 of the middle portion 5.
  • the diameter DS is at least equal or slightly higher than the greater diameter of the rifling of a suitable gun or handgun barrel (diameter of the grooves). This is because to obtain a close sealing of the propellant from the nuzzle during traveling of the projectile 1 through the barrel.
  • circular grooves 12 are provided at least in a rearward direction adjacent to the sealing rings 10 and 11.
  • circular grooves 13 may also be formed in the frontward direction of the sealing rings 10 and 11.
  • the outer diameter DGr of these grooves 12, 13 are lower than the outer diameter DS of the sealing rings 10, 11 and the outer diameter D1 of the middle portion 5.
  • Fig. 2 shows a cross sectional shape of the sealing rings 10 and 11, which has a sort of an ogive shape with a blunted or cylindrical circumferential middle section (see details in Fig. 2A ).
  • Other suitable profile shapes are the following: rectangular, semi-circular, trapezoid, ellipsoid.
  • the forward facing 10b and rearward facing surface 10a sections are formed symmetrically according to the embodiment shown in Fig. 2 . However, it is possible to form these surface sections differently. Either to obtain better inner ballistic properties (improved sealing, improved forming properties, improved propulsion properties) and/or improved outer ballistic properties (improved aerodynamical behaviour).
  • Fig. 3 shows a third embodiment of a projectile 1 according to the present invention. Its shape corresponds to the shape of those projectiles shown in Fig. 1 or Fig. 3 .
  • the base portion 4 or boat-tail section carries a number of fins 16, which extend radially from the longitudinal axis 2. They are inclined by an angle of 10° to 30 ° in relation to the longitudinal axis 2 (angle ⁇ ).
  • the outer diameter of the fins D2 is less than the outer diameter D1 of the middle portion 5. This avoids any contact with the barrel lands and grooves during propulsion.
  • these fins 16 are bended and have a curved shape with a radius RF.
  • the inclination in the rearward direction may be either counter clockwise ( Fig.
  • Fig. 3a shows an embodiment with eight fins 16, which are inclined counter clockwise. Further embodiments may have less (at least two) or more fins 16.
  • Fig. 4 shows a fourths embodiment of a projectile 1 according to the present invention in which longitudinal flutes 17 are arranged in the nose portion 3.
  • the flutes 17 are arranged equally interspaced in a circumferential direction. In a further embodiment (not shown) these flutes may also be arranged in the middle portion 5 of the projectile 1.
  • Each flute is tapered and has a triangular cross section (see section AA in Fig. 4 ) with a tip of the triangular section pointing to the center of the projectile 1.
  • the maximum depth DG equals 0.025 to 0.4 times of the diameter D1 and the curved bottom line has a radius RB, which equals 0.25 to 25 times of the diameter D1.
  • a tip section 19 with the length L4 is provided, which is free of a flute arrangement.
  • Fig. 4a and Fig. 4b show different shapes and sizes of possible flute arrangements.
  • Fig. 4a shows an arrangement with only four flutes 17a and
  • Fig. 4b shows a high number of flutes 17b, which are arranged with a very low depth DG.
  • Fig. 5 to Fig. 5d show different dimple arrangements, which are either arranged in the nose portion 3 and/or in the base portion 4.
  • the dimples 20 have a spherical segment shape with a base diameter DB and a depth d (see detail 5f), wherein the base diameter DB equals 0.05 to 0.3 times of the diameter D1 and the depth d equals 0.015 to 0.13 times the diameter D1.
  • the dimples 20 can be arranged so that the outer edges can be either touching or not touching.
  • the dimples 20 can have a center-to-center distance DC ranging from 1 to 2 times the base diameter DB, depending on the dimple size and pattern.
  • Figs. 5 and 5b show different arrangement and sizes of dimples 20 in the base portion 4, wherein the dimples are arranged in circles, which are displaced to each other in a circumferential direction to allow for a denser arrangement of the dimples.
  • Figs. 5a and 5c show a similar arrangement in which the circles are aligned so that rows of dimples 20 occur.
  • Figs. 5a and 5d show different sizes and arrangement of dimples 20, wherein the dimples 20 are arranged in the nose portion 3 and the base portion 4 and Fig. 5e shows an arrangement, where dimples 20 are only arranged in the nose portion.
  • Figure 6 shows an exploded section view of an armor-piercing projectile 101 according to a sixth embodiment having an outer component 102, an inner component 103 and a cap 104.
  • an outer component 102 Inside the outer component 102 a cavity 105 is formed into the outer component 102 matching the outer dimension of the inner component 103.
  • the cap 104 seals the inner component 103 inside the outer component 102.
  • the inner component 103 or penetrator is pressed into the cavity 105 and the cap 104 is pressed into the recess 106, which is formed at the rear end of the cavity 105 to keep the inner component 103 (penetrator) inside the outer component 102.
  • This arrangement forms the armor-piercing projectile 101.
  • the cavity 105 is formed into the nose portion 3 of the outer component 102.
  • the cavity 105 and the inner component 103 correspond exactly to each other in shape and dimensions.
  • the outer component 102 is made from a homogenous material specifically metallic material. Suitable materials for the outer component include copper, copper alloys and other similar materials which is softer than the material of the fire arm barrel from which the projectile is fired.
  • the inner component 103 is made from a material with a higher density than the material of the outer component 102. Suitable materials for the inner component 103 include solid tungsten, tungsten carbide, nanotechnical materials such as nano steel and others.
  • a seventh embodiment of a projectile 1 according to the present invention where all the above mentioned features are combined into one projectile 1.
  • a dimple arrangement in the base portion 4 a first and a second ductile annular sealing area in the middle portion 5 and a flute arrangement in the nose portion 3.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP17196685.6A 2017-10-16 2017-10-16 Projectile d'armes de petite taille Withdrawn EP3470769A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP17196685.6A EP3470769A1 (fr) 2017-10-16 2017-10-16 Projectile d'armes de petite taille
MX2017014723A MX2017014723A (es) 2017-10-16 2017-11-16 Proyectil de armas pequeñas.
US15/919,307 US20190113318A1 (en) 2017-10-16 2018-03-13 Small arms projectile

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17196685.6A EP3470769A1 (fr) 2017-10-16 2017-10-16 Projectile d'armes de petite taille

Publications (1)

Publication Number Publication Date
EP3470769A1 true EP3470769A1 (fr) 2019-04-17

Family

ID=60117601

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17196685.6A Withdrawn EP3470769A1 (fr) 2017-10-16 2017-10-16 Projectile d'armes de petite taille

Country Status (3)

Country Link
US (1) US20190113318A1 (fr)
EP (1) EP3470769A1 (fr)
MX (1) MX2017014723A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210108903A1 (en) * 2017-10-17 2021-04-15 Smart Nanos, Llc Multifunctional composite projectiles and methods of manufacturing the same

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2753190A1 (es) * 2019-10-16 2020-04-07 Extreme Polymer Res S L Proyectil para armas de fuego
US11181352B1 (en) * 2020-06-28 2021-11-23 Daniel J. Smitchko Firearm projectile
US11519704B1 (en) * 2020-12-01 2022-12-06 Apex Outdoors Llc Monolithic bullet
CN113028908A (zh) * 2021-04-21 2021-06-25 东北大学 一种水下旋转稳定的超空泡枪弹

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US871825A (en) * 1906-09-07 1907-11-26 Ludwig Schupmann Projectile for rifled firearms.
DE29516889U1 (de) * 1995-04-27 1996-01-25 Bofors Carl Gustaf Ab Überkalibriges Gewehrgeschoß
US6629669B2 (en) 2001-06-14 2003-10-07 Warren S. Jensen Controlled spin projectile
WO2013020976A1 (fr) * 2011-08-08 2013-02-14 Ruag Ammotec Gmbh Structuration de la surface de l'ogive d'un projectile
US8573129B1 (en) 2010-01-07 2013-11-05 Daniel J. Smitchko Self sealing firearm projectile
US20160153757A1 (en) * 2014-04-30 2016-06-02 Joshua Mahnke Projectile with Enhanced Ballistics

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US871825A (en) * 1906-09-07 1907-11-26 Ludwig Schupmann Projectile for rifled firearms.
DE29516889U1 (de) * 1995-04-27 1996-01-25 Bofors Carl Gustaf Ab Überkalibriges Gewehrgeschoß
US6629669B2 (en) 2001-06-14 2003-10-07 Warren S. Jensen Controlled spin projectile
US8573129B1 (en) 2010-01-07 2013-11-05 Daniel J. Smitchko Self sealing firearm projectile
WO2013020976A1 (fr) * 2011-08-08 2013-02-14 Ruag Ammotec Gmbh Structuration de la surface de l'ogive d'un projectile
US20160153757A1 (en) * 2014-04-30 2016-06-02 Joshua Mahnke Projectile with Enhanced Ballistics

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210108903A1 (en) * 2017-10-17 2021-04-15 Smart Nanos, Llc Multifunctional composite projectiles and methods of manufacturing the same
US11821714B2 (en) * 2017-10-17 2023-11-21 Smart Nanos, Llc Multifunctional composite projectiles and methods of manufacturing the same

Also Published As

Publication number Publication date
US20190113318A1 (en) 2019-04-18
MX2017014723A (es) 2019-04-17

Similar Documents

Publication Publication Date Title
EP3470769A1 (fr) Projectile d'armes de petite taille
US11118883B2 (en) Projectile with enhanced ballistic efficiency
US11808550B2 (en) Projectile with enhanced ballistics
US8151710B2 (en) Surface ship, deck-launched anti-torpedo projectile
US11549789B2 (en) Optimized subsonic projectiles
US8893621B1 (en) Projectile
US10126105B2 (en) Projectiles for ammunition and methods of making and using the same
US20090308275A1 (en) Projectile for fire arms
US20090064888A1 (en) Cavitating core
RU2597431C2 (ru) Пуля боеприпаса стрелкового оружия
US10378867B2 (en) Cartridge
US20220381542A1 (en) Solid bullet, intermediate product for manufacturing a solid bullet, and method for producing a solid bullet
US20180120069A1 (en) Projectile
JP2020536215A (ja) 増強性能弾薬
CA2867553A1 (fr) Ogive de missile
US2234165A (en) Projectile
US2103155A (en) Projectile
US7096791B2 (en) Projectile with improved dynamic shape
US20220307806A1 (en) Bullet Stabilization in Subsonic Flight
RU2075035C1 (ru) Пуля
EP1563247B1 (fr) Obus de mortier a portee accrue

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20191017

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

17Q First examination report despatched

Effective date: 20200128

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20200609